US8205454B2 - Convergent divergent nozzle with edge cooled divergent seals - Google Patents
Convergent divergent nozzle with edge cooled divergent seals Download PDFInfo
- Publication number
- US8205454B2 US8205454B2 US11/671,591 US67159107A US8205454B2 US 8205454 B2 US8205454 B2 US 8205454B2 US 67159107 A US67159107 A US 67159107A US 8205454 B2 US8205454 B2 US 8205454B2
- Authority
- US
- United States
- Prior art keywords
- divergent
- skin
- seal
- divergent seal
- longitudinal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 238000001816 cooling Methods 0.000 claims abstract description 53
- 125000006850 spacer group Chemical group 0.000 claims description 13
- 239000007789 gas Substances 0.000 description 16
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003190 augmentative effect Effects 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000010339 dilation Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
- F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S277/00—Seal for a joint or juncture
- Y10S277/93—Seal including heating or cooling feature
Definitions
- the present invention relates to gas turbine engines having convergent/divergent nozzles, and more particularly to a cooled divergent seal arrangement.
- An exhaust nozzle optimizes the thrust produced within a gas turbine engine.
- convergent/divergent (C/D) nozzles provide a multitude of nozzle positions. Flaps circumferentially distributed aft of the augmentor or exhaust duct form the convergent and divergent sections for which the nozzle is named. Flap seals disposed between adjacent flaps minimize gas leakage between flaps in both sections.
- the convergent section is pivotally connected to the augmentor or exhaust duct and to the divergent section.
- the divergent section is pivotally connected to the convergent section and to an external fairing positioned radially outboard of the divergent section. The opposite end of the external fairing is pivotally attached to a static outer casing which surrounds a portion of the nozzle. Together, the outer casing, the convergent and divergent sections, and the external fairing form a nozzle plenum.
- exhaust nozzles are cooled with air bled at lower temperature and a higher pressure than that of the exhaust gas flow passing through the nozzle system. Cooling air enters the exhaust gas path within the augmentor or exhaust duct via cooling holes in the augmentor or exhaust duct liner and subsequently passes into the nozzle system as a layer of cooling airflow along the inner surface or “hot side” of the nozzle flaps and seals. Cooling airflow within the nozzle plenum also cools the “cold side” side of the flaps and flap seals.
- the nozzle system includes a plurality of circumferentially distributed convergent flaps, divergent flaps, convergent seals and divergent seals which circumscribe an engine centerline and define the radial outer boundary of a core gas path.
- the flaps and seals define a convergent section and a divergent section of the nozzle with the throat or jet area defined therebetween.
- Each convergent seal is pivotably connected to the stationary frame with each divergent seal pivotably connected at a joint at an aft end section of the convergent seal.
- Each divergent seal includes a body, a spine member along a seal longitudinal axis, a joint structure and a flap position guide.
- Each divergent seal includes a multiple of divergent seal intakes in a forward end section downstream of a divergent hinge axis to receive a portion of the cooling airflow.
- Each divergent seal body is manufactured of a hot sheet inner skin and a cold sheet outer skin. The skins form a multiple of longitudinal channels therebetween.
- the longitudinal channels communicate with a multiple of divergent seal edge channels formed within a longitudinal side or sides of each divergent seal.
- the multiple of edge channels are raked aft.
- the cooling airflow from the longitudinal channels is communicated through the multiple of edge channels to cool the edges of the divergent seals as well as the gas path surface of the adjacent divergent flaps.
- the present invention therefore provides cooling of the divergent sections while efficiently utilizing the cooling air.
- FIG. 1A is a general perspective view of a variable geometry exhaust nozzle of the present invention with the nozzle shown in a maximum position;
- FIG. 1B is a general perspective view of a variable geometry exhaust nozzle of the present invention with the nozzle shown in a minimum position;
- FIG. 2A is a general sectional side view of a variable geometry exhaust nozzle of the present invention with the nozzle shown in a maximum position which corresponds with FIG. 1A , the nozzle being illustrated on only one side of its centerline;
- FIG. 2B is a general sectional side view of a variable geometry exhaust nozzle of the present invention with the nozzle shown in a minimum position which corresponds with FIG. 1B , the nozzle being illustrated on only one side of its centerline;
- FIG. 3A is a general frontal perspective view of a divergent section of the variable geometry exhaust nozzle from a cold side with an external flap removed shown in a maximum position;
- FIG. 3B is a general frontal perspective view of a divergent section of the variable geometry exhaust nozzle from a cold side with an external flap removed shown in a minimum position;
- FIG. 4A is a general perspective partial phantom view of a segment of the variable geometry exhaust nozzle of the present invention with the nozzle shown in a maximum position;
- FIG. 4B is a general perspective partial phantom view of a segment of the variable geometry exhaust nozzle of the present invention with the nozzle shown in a minimum position;
- FIG. 5 is a general aft perspective external view of a divergent section of the variable geometry exhaust nozzle
- FIG. 6A is a general perspective view of a convergent section from a “hot” side.
- FIG. 6B is a general perspective view of a convergent section from a “hot” side at a joint to which the divergent sections attach;
- FIG. 7 is a section view of the divergent seal-divergent flap interface taken along the line 7 - 7 in FIG. 6A ;
- FIG. 8A is a general perspective view of a divergent seal according to the present invention from a “cold” side;
- FIG. 8B is an expanded partial phantom perspective view of edge channels within the divergent seal
- FIG. 8C is an expanded side view of the edge channels.
- FIG. 9 is a perspective view of the divergent seal being assembled with a spacer comb utilized to form the multiple of edge channels with a multiple of spacer teeth.
- FIGS. 1A and 1B illustrate a nozzle system 10 for a gas turbine engine.
- FIG. 1A depicts the nozzle 10 in a maximum dilated position (also illustrated in FIG. 2A ), which is typical during afterburning operation
- FIG. 1B depicts the nozzle system 10 in a minimal dilated position ( FIG. 2B ), which is typical during non-afterburning operation.
- the nozzle includes a plurality of circumferentially distributed convergent flaps 12 (only one shown in section), each pivotably connected to a stationary frame 14 having a cooling liner panel 16 upstream thereof.
- a plurality of circumferentially distributed divergent flaps 18 are pivotably connected at a joint structure 20 to an aft end section of the convergent flaps 12 .
- a plurality of divergent seals 21 are each pivotally connected to a respective convergent seal 23 which are respectively distributed circumferentially between each of the divergent flap 18 and convergent flap 12 pairs.
- Each convergent seal 23 is pivotably connected to the stationary frame 14 with each divergent seal 21 pivotably connected at a joint structure 42 ( FIGS. 7A and 7B ) adjacent an aft end section of each convergent seal 23 .
- the convergent and divergent flaps 12 , 18 and the convergent and divergent seals 21 , 23 circumscribe the nozzle centerline A to define the radial outer boundary of a combustion gas path F ( FIGS. 1A , 1 B).
- a control system (illustrated schematically) governs the angular orientations of the convergent flaps 12 and divergent flaps 18 to adjust the nozzle throat area 34 and exit area 26 ( FIGS. 2A , 2 B).
- the flaps 12 , 18 and seals 21 , 23 define a convergent section 30 and a divergent section 32 of the nozzle with the throat area 34 defined therebetween.
- the throat area 34 is the minimum cross sectional area of the nozzle which when compared to the nozzle exit area 26 defines a nozzle area ratio.
- the liner panels 16 taken collectively (also illustrated in FIG. 7A ), form a liner that cooperates with the convergent flaps 12 and convergent seals 23 to define an annular cooling airflow passageway 28 .
- the passageway 28 guides a cooling airflow (illustrated schematically by arrows C) along an inner surface of the convergent flaps 12 and convergent seals 23 .
- the cooling airflow C is typically sourced from fan bypass airflow and/or other airflow that is different from the exhaust gas flow (illustrated schematically by arrow F).
- the cooling airflow C at least partially shields the flaps 12 , 18 and seals 21 , 23 from the intense heat of the exhaust gas flow F.
- a divergent flap-seal section 36 (also illustrated in FIG. 5 ) which includes one divergent seal 21 with one divergent flap 18 (the opposite side divergent flap 18 position illustrated by only the plow tip section 73 ).
- One divergent flap 18 is located to overlap each divergent seal 21 longitudinal side 54 , 56 .
- the flap-seal section 36 as illustrated herein is for descriptive purposes and that the description applies to each adjacent flap 18 and seal 21 defined about the circumference of the nozzle 10 .
- the flap-seal section 36 is illustrated from a “cold-side” opposite the “hot-side” (illustrated in FIGS. 7A and 7B ).
- the “hot-side” of the flap-seal section 36 is directly exposed to the exhaust gases flow which exits the engine.
- the “cold-side” of the flap-seal section 36 is defined as the side opposite the exhaust gas flow path F.
- Each divergent seal 21 generally includes a divergent seal body 38 , a spine member 40 along a seal longitudinal axis L, a seal joint structure 42 and a flap position guide 44 .
- the seal joint structure 42 forms a portion of the joint structure 20 that defines a hinge axis H that surrounds the engine centerline A ( FIGS. 2A and 2B ).
- the divergent seal body 38 may be described as having a length 46 , defined as extending between a forward end section 48 and an aft end section 50 ; and a width 52 defined between the first longitudinal side 54 and the second longitudinal side 56 (also illustrated in FIG. 5 ).
- the divergent seal body 38 is preferably a relatively planar member having a multitude of structural corrugations 57 or the like. Corrugation geometries other than that illustrated may also be utilized with the present invention.
- the aft end section 50 is preferably of a chevron shape to form a serrated nozzle end ( FIGS. 1A and 1B ).
- Each divergent flap 18 may be described as having a divergent flap body 60 , defined as extending between a forward end section 62 and an aft end section 64 ; and a width 66 defined between a first longitudinal side 68 and a second longitudinal side 70 ( FIG. 5 ).
- the divergent flap body 60 is preferably manufactured of a solid ceramic matrix composite material, but may alternatively be formed as a metallic “cold sheet,” “hot sheet” assembly.
- the forward end section 62 of each divergent flap 18 includes the divergent flap joint structure 69 that forms a portion of the joint structure 20 ( FIGS. 2A , 2 B).
- the divergent flap joint structure 69 corresponds with the divergent seal joint structure 42 along the hinge axis H (also illustrated in FIGS. 6A and 6B ).
- each divergent flap 18 includes a plow tip section 73 .
- the plow tip section 73 is preferably chiseled and includes a hinge point 77 for attachment of an external flap 79 ( FIGS. 4A and 4B ). It should be understood that various plow tip sections planforms and profiles will be usable with the present invention.
- Each divergent flap 18 preferably includes a forward bridge support 76 and an aft bridge support 78 which respectively receive a forward seal bridge bracket 80 and an aft seal bridge bracket 82 mounted to the divergent seal 21 .
- the forward seal bridge bracket 80 and the aft seal bridge bracket 82 of the divergent seal 21 respectively engage the forward bridge support 76 and the aft bridge support 78 mounted to the adjacent divergent flaps 18 .
- the forward seal bridge bracket 80 and the aft seal bridge bracket 82 on the divergent seal 21 bridge the forward bridge support 76 and the aft bridge support 78 of two adjacent divergent flaps 18 to link movement between adjacent divergent flaps 18 and divergent seals 21 around the circumference of the nozzle 10 .
- the interface of the forward seal bridge bracket 80 and the aft seal bridge bracket 82 with the forward bridge support 76 and the aft bridge support 78 provides for axial and radial support for the divergent seal 21 between the adjacent divergent flaps 18 .
- the forward seal bridge bracket 80 provides for axial and radial support for the divergent seal 21 between the adjacent divergent flaps 18 while the aft seal bridge bracket 82 need provide only radial support.
- the combined axial and radial support are provided by the sliding interface between the forward seal bridge bracket 80 , the aft seal bridge bracket 82 and the respective forward bridge support 76 and aft bridge support 78 rather than at the hinge line H.
- a centering linkage assembly 83 is restrained by the flap position guide 44 to further guide dilation of the nozzle system 10 during articulation between the maximum dilated position and the minimal dilated position to facilitate generally synchronous movement between the divergent flaps 18 and divergent seals 21 . It should be understood that various linkages and guides are alternatively or additionally usable with the present invention.
- each divergent seal 21 at least partially overlaps the inner side of each adjacent divergent flap 18 .
- the divergent seals 21 form an inner layer within an outer layer defined by the divergent flaps 18 in which a divergent seal 21 overlaps each gap between two adjacent divergent flaps 18 relative the nozzle centerline A.
- the flap seal joint structure 42 includes a horn 86 and a fork 88 .
- the forward bridge bracket retain each divergent seal 21 in the axial direction, there is no need for axial sliding of the divergent seal 21 relative to the divergent flap 18 .
- the horn 86 is mounted adjacent an aft end of the convergent seal 23 ( FIG. 6B ).
- the fork 88 is mounted adjacent the forward end section 48 of the divergent seal 21 .
- the fork 88 includes a tine 90 a , 90 b ( FIG. 3B ) arranged on either side of the seal longitudinal axis L.
- the horn 86 extends between the tines 90 a , 90 b and need only provide circumferential support as the axial and radial support are provided by the sliding interface between the forward seal bridge bracket 80 , the aft seal bridge bracket 82 and the respective forward bridge support 76 and aft bridge support 78 .
- Each divergent seal 21 includes a multiple of divergent seal intakes 100 (also illustrated in FIG. 7 ) in the forward end section 48 arranged downstream of the hinge axis H to receive a portion of the cooling airflow C.
- Each divergent seal body 38 is manufactured of a metallic hot sheet inner skin 102 and a metallic cold sheet outer skin 104 ( FIG. 7 ).
- the skins 102 , 104 form a multiple of longitudinal channels 106 therebetween ( FIG. 8A ).
- the longitudinal channels 106 may at least partially be defined by the spine member 40 along a seal longitudinal axis L ( FIG. 7 ).
- the longitudinal channels 106 preferably communicate with a multiple of edge channels 108 ( FIGS. 8B and 8C ) formed within the first longitudinal side 54 and the second longitudinal side 56 of each divergent seal 21 .
- the multiple of edge channels 108 are preferably located transverse to the longitudinal axis L and most preferably are raked aft. It should be understood that the multiple of edge channels 108 may be formed along either or both of the first longitudinal side 54 and the second longitudinal side 56 of each divergent seal 21 as well as raked in other directions and configurations.
- the cooling airflow C from the longitudinal channels 106 is communicated through the multiple of edge channels 108 to thereby cool the first longitudinal side 54 (and alternatively or additionally the second longitudinal side 56 ) of each divergent seal 21 as well as the gas path surface of the adjacent divergent flaps 18 .
- the cooling airflow C may be directed from the edge channels 108 to circumscribe the inner periphery of the nozzle system 10 to further film cool the divergent seals 21 and divergent flaps 18 .
- Cooling airflow may additionally be communicated through a multiple of surface holes 110 which are typically laser drilled and located through the hot inner skin 102 ( FIG. 6A ).
- the surface holes 110 facilitate further cooling of the gas path surface of each divergent seal 21 .
- the divergent seal 21 is preferably manufactured by attaching a spacer comb 112 having a multiple of spacer teeth 114 between the inner skin 102 and the outer skin 104 though spot laser welding at welds W or the like.
- the spacer comb 112 is preferably attached while the inner skin 102 , the outer skin 104 and the longitudinal spline 40 are assembled. Once assembled, the spacer comb 112 is trimmed away to leave the multiple of spacer teeth 114 ( FIG. 8C ) welded in place to thereby define the multiple of edge channels 108 . That is, the spacer teeth 114 separate the inner skin 102 and the outer skin 104 so as to define the edge channels 109 therebetween.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Gasket Seals (AREA)
Abstract
Description
Claims (29)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/671,591 US8205454B2 (en) | 2007-02-06 | 2007-02-06 | Convergent divergent nozzle with edge cooled divergent seals |
EP08250298.0A EP1956225B1 (en) | 2007-02-06 | 2008-01-24 | Convergent-divergent nozzle with edge cooled divergent seals |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/671,591 US8205454B2 (en) | 2007-02-06 | 2007-02-06 | Convergent divergent nozzle with edge cooled divergent seals |
Publications (2)
Publication Number | Publication Date |
---|---|
US20090072490A1 US20090072490A1 (en) | 2009-03-19 |
US8205454B2 true US8205454B2 (en) | 2012-06-26 |
Family
ID=39100224
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/671,591 Active 2031-12-17 US8205454B2 (en) | 2007-02-06 | 2007-02-06 | Convergent divergent nozzle with edge cooled divergent seals |
Country Status (2)
Country | Link |
---|---|
US (1) | US8205454B2 (en) |
EP (1) | EP1956225B1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130232949A1 (en) * | 2012-03-09 | 2013-09-12 | Gary J. Dillard | Pressure balanced area control of high aspect ratio nozzle |
US20150292437A1 (en) * | 2013-04-12 | 2015-10-15 | United Technologies Corporation | Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface |
US20160017815A1 (en) * | 2013-03-12 | 2016-01-21 | United Technologies Corporation | Expanding shell flow control device |
US9845768B2 (en) | 2013-03-13 | 2017-12-19 | Rolls-Royce North American Technologies, Inc. | Three stream, variable area, vectorable nozzle |
US20180156053A1 (en) * | 2011-06-30 | 2018-06-07 | United Technologies Corporation | Impingement cooled nozzle liner |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9163582B2 (en) | 2012-05-30 | 2015-10-20 | United Technologies Corporation | Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction |
US8695540B2 (en) | 2012-06-18 | 2014-04-15 | Aerojet Rocketdyne Of De, Inc. | Fuel-cracking diesel engine system |
EP2998556B1 (en) | 2013-05-15 | 2021-10-13 | IHI Corporation | Variable nozzle for aeronautic gas turbine engine |
EP3008320B1 (en) * | 2013-06-14 | 2020-07-29 | Saab Ab | Variable-geometry convergent-divergent exhaust nozzle for a jet engine and method for varying the nozzle |
WO2015112554A1 (en) * | 2014-01-24 | 2015-07-30 | United Technologies Corporation | Divergent flap |
GB201800857D0 (en) * | 2018-01-19 | 2018-03-07 | Rolls Royce Plc | Aircraft nozzle |
CN211874765U (en) * | 2018-11-29 | 2020-11-06 | 曾固 | Centrifugal through-flow high-jet-speed water and mist injection device |
FR3100284B1 (en) * | 2019-08-30 | 2021-12-03 | Safran Aircraft Engines | COUPLE CONVERGENT-DIVERGENT FLAP FOR VARIABLE GEOMETRY TURBOREACTOR NOZZLE WHOSE SHUTTERS EACH INCLUDE A COOLING AIR CIRCULATION DUCT |
Citations (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4203286A (en) | 1976-08-27 | 1980-05-20 | The United States Of America As Represented By The Secretary Of The Air Force | Cooling apparatus for an exhaust nozzle of a gas turbine engine |
US4643356A (en) | 1977-08-31 | 1987-02-17 | United Technologies Corporation | Cooling liner for convergent-divergent exhaust nozzle |
US4718230A (en) | 1986-11-10 | 1988-01-12 | United Technologies Corporation | Augmentor liner construction |
US4747543A (en) | 1987-04-14 | 1988-05-31 | United Technologies Corporation | Nozzle flap cooling liner |
US4747542A (en) | 1987-04-14 | 1988-05-31 | United Technologies Corporation | Nozzle flap edge cooling |
US5000386A (en) | 1989-07-03 | 1991-03-19 | General Electric Company | Exhaust flaps |
US5060472A (en) | 1990-04-12 | 1991-10-29 | The United States Of America As Represented By The Secretary Of The Air Force | Insulated cooling liner |
US5067324A (en) | 1990-04-04 | 1991-11-26 | United Technologies Corporation | Engine nozzle liner retainer |
US5076496A (en) | 1990-02-05 | 1991-12-31 | General Electric Company | Exhaust nozzle flap seal |
US5080284A (en) | 1990-06-25 | 1992-01-14 | United Technologies Corporation | Cooling system for the trailing edge of a liner |
US5111992A (en) | 1991-04-19 | 1992-05-12 | United Technologies Corporation | Variable throat convergent/divergent nozzle |
US5131222A (en) | 1990-11-28 | 1992-07-21 | The United States Of Americas As Represented By The Secretary Of The Air Force | Thermally valved cooling system for exhaust nozzle systems |
US5141154A (en) | 1991-04-22 | 1992-08-25 | United Technologies Corporation | Variable throat convergent/divergent nozzle |
US5188292A (en) | 1991-06-28 | 1993-02-23 | The United States Of America As Represented By The Secretary Of The Air Force | Thermal shields for rotating members in a gas flow path |
US5209059A (en) | 1991-12-27 | 1993-05-11 | The United States Of America As Represented By The Secretary Of The Air Force | Active cooling apparatus for afterburners |
US5215256A (en) | 1992-07-16 | 1993-06-01 | Barcza W Kevin | Flap hinge arrangement for a convergent/divergent nozzle |
US5239815A (en) | 1991-09-23 | 1993-08-31 | United Technologies Corporation | Sync-ring assembly for a gas turbine engine exhaust nozzle |
US5239823A (en) | 1991-02-26 | 1993-08-31 | United Technologies Corporation | Multiple layer cooled nozzle liner |
US5249419A (en) | 1992-10-07 | 1993-10-05 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle liner for gas turbine engines |
US5255849A (en) | 1991-11-05 | 1993-10-26 | General Electric Company | Cooling air transfer apparatus for aircraft gas turbine engine exhaust nozzles |
US5269467A (en) | 1992-08-03 | 1993-12-14 | General Electric Company | Vectoring exhaust nozzle seal and flap retaining apparatus |
US5364029A (en) | 1993-08-30 | 1994-11-15 | United Technologies Corporation | Axisymmetric convergent/divergent nozzle with external flaps |
US5437411A (en) | 1992-12-14 | 1995-08-01 | General Electric Company | Vectoring exhaust nozzle flap and seal positioning apparatus |
US5522546A (en) | 1994-08-19 | 1996-06-04 | General Electric Company | Variable exhaust nozzle seal |
US5524438A (en) | 1994-12-15 | 1996-06-11 | United Technologies Corporation | Segmented bulkhead liner for a gas turbine combustor |
US5560198A (en) | 1995-05-25 | 1996-10-01 | United Technologies Corporation | Cooled gas turbine engine augmentor fingerseal assembly |
US5586431A (en) | 1994-12-06 | 1996-12-24 | United Technologies Corporation | Aircraft nacelle ventilation and engine exhaust nozzle cooling |
US5683034A (en) | 1995-05-22 | 1997-11-04 | United Technologies Corporation | Engine exhaust nozzle seal |
US5775589A (en) | 1991-11-05 | 1998-07-07 | General Electric Company | Cooling apparatus for aircraft gas turbine engine exhaust nozzles |
US5794851A (en) | 1995-12-07 | 1998-08-18 | United Technologies Corporation | Nozzle sealing apparatus |
US5797544A (en) | 1996-09-27 | 1998-08-25 | United Technologies Corporation | C/D nozzle with synchronizing ring link suspension |
US5799874A (en) | 1995-11-30 | 1998-09-01 | United Technologies Corporation | Aerodynamically controlled ejector |
US5813611A (en) | 1996-09-27 | 1998-09-29 | United Technologies Corporation | Compact pressure balanced fulcrum-link nozzle |
US5833139A (en) | 1995-09-06 | 1998-11-10 | United Technologies Corporation | Single variable flap exhaust nozzle |
US5839663A (en) | 1996-07-23 | 1998-11-24 | United Technologies Corporation | Gas turbine exhaust nozzle flap and flap seal apparatus |
US6142416A (en) | 1994-09-29 | 2000-11-07 | General Electric Company | Hydraulic failsafe system and method for an axisymmetric vectoring nozzle |
US6301877B1 (en) | 1995-11-13 | 2001-10-16 | United Technologies Corporation | Ejector extension cooling for exhaust nozzle |
US6347510B1 (en) | 1998-12-18 | 2002-02-19 | United Technologies Corporation | Axi-nozzle ejector seal |
US6398129B1 (en) | 1999-12-29 | 2002-06-04 | United Technologies Corporation | Throat configuration for axisymmetric nozzle |
US6607355B2 (en) | 2001-10-09 | 2003-08-19 | United Technologies Corporation | Turbine airfoil with enhanced heat transfer |
US6993914B2 (en) * | 2003-08-12 | 2006-02-07 | Snecma Moteurs | Convergent-divergent turbojet nozzle |
US7032835B2 (en) * | 2004-01-28 | 2006-04-25 | United Technologies Corporation | Convergent/divergent nozzle with modulated cooling |
US20060266016A1 (en) * | 2005-05-27 | 2006-11-30 | United Technologies Corporation | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle |
US20070186555A1 (en) * | 2006-02-15 | 2007-08-16 | United Technologies Corporation | Convergent divergent nozzle with supported divergent seals |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5111550A (en) * | 1991-05-06 | 1992-05-12 | United Technologies Corporation | Hinged fluid passage assembly |
US5484105A (en) * | 1994-07-13 | 1996-01-16 | General Electric Company | Cooling system for a divergent section of a nozzle |
-
2007
- 2007-02-06 US US11/671,591 patent/US8205454B2/en active Active
-
2008
- 2008-01-24 EP EP08250298.0A patent/EP1956225B1/en not_active Ceased
Patent Citations (46)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4203286A (en) | 1976-08-27 | 1980-05-20 | The United States Of America As Represented By The Secretary Of The Air Force | Cooling apparatus for an exhaust nozzle of a gas turbine engine |
US4643356A (en) | 1977-08-31 | 1987-02-17 | United Technologies Corporation | Cooling liner for convergent-divergent exhaust nozzle |
US4718230A (en) | 1986-11-10 | 1988-01-12 | United Technologies Corporation | Augmentor liner construction |
US4747543A (en) | 1987-04-14 | 1988-05-31 | United Technologies Corporation | Nozzle flap cooling liner |
US4747542A (en) | 1987-04-14 | 1988-05-31 | United Technologies Corporation | Nozzle flap edge cooling |
US5000386A (en) | 1989-07-03 | 1991-03-19 | General Electric Company | Exhaust flaps |
US5076496A (en) | 1990-02-05 | 1991-12-31 | General Electric Company | Exhaust nozzle flap seal |
US5067324A (en) | 1990-04-04 | 1991-11-26 | United Technologies Corporation | Engine nozzle liner retainer |
US5060472A (en) | 1990-04-12 | 1991-10-29 | The United States Of America As Represented By The Secretary Of The Air Force | Insulated cooling liner |
US5080284A (en) | 1990-06-25 | 1992-01-14 | United Technologies Corporation | Cooling system for the trailing edge of a liner |
US5131222A (en) | 1990-11-28 | 1992-07-21 | The United States Of Americas As Represented By The Secretary Of The Air Force | Thermally valved cooling system for exhaust nozzle systems |
US5239823A (en) | 1991-02-26 | 1993-08-31 | United Technologies Corporation | Multiple layer cooled nozzle liner |
US5111992A (en) | 1991-04-19 | 1992-05-12 | United Technologies Corporation | Variable throat convergent/divergent nozzle |
US5141154A (en) | 1991-04-22 | 1992-08-25 | United Technologies Corporation | Variable throat convergent/divergent nozzle |
US5188292A (en) | 1991-06-28 | 1993-02-23 | The United States Of America As Represented By The Secretary Of The Air Force | Thermal shields for rotating members in a gas flow path |
US5239815A (en) | 1991-09-23 | 1993-08-31 | United Technologies Corporation | Sync-ring assembly for a gas turbine engine exhaust nozzle |
US5255849A (en) | 1991-11-05 | 1993-10-26 | General Electric Company | Cooling air transfer apparatus for aircraft gas turbine engine exhaust nozzles |
US5775589A (en) | 1991-11-05 | 1998-07-07 | General Electric Company | Cooling apparatus for aircraft gas turbine engine exhaust nozzles |
US5209059A (en) | 1991-12-27 | 1993-05-11 | The United States Of America As Represented By The Secretary Of The Air Force | Active cooling apparatus for afterburners |
US5215256A (en) | 1992-07-16 | 1993-06-01 | Barcza W Kevin | Flap hinge arrangement for a convergent/divergent nozzle |
US5269467A (en) | 1992-08-03 | 1993-12-14 | General Electric Company | Vectoring exhaust nozzle seal and flap retaining apparatus |
US5249419A (en) | 1992-10-07 | 1993-10-05 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle liner for gas turbine engines |
US5437411A (en) | 1992-12-14 | 1995-08-01 | General Electric Company | Vectoring exhaust nozzle flap and seal positioning apparatus |
US5364029A (en) | 1993-08-30 | 1994-11-15 | United Technologies Corporation | Axisymmetric convergent/divergent nozzle with external flaps |
US5522546A (en) | 1994-08-19 | 1996-06-04 | General Electric Company | Variable exhaust nozzle seal |
US6142416A (en) | 1994-09-29 | 2000-11-07 | General Electric Company | Hydraulic failsafe system and method for an axisymmetric vectoring nozzle |
US5586431A (en) | 1994-12-06 | 1996-12-24 | United Technologies Corporation | Aircraft nacelle ventilation and engine exhaust nozzle cooling |
US5524438A (en) | 1994-12-15 | 1996-06-11 | United Technologies Corporation | Segmented bulkhead liner for a gas turbine combustor |
US5683034A (en) | 1995-05-22 | 1997-11-04 | United Technologies Corporation | Engine exhaust nozzle seal |
US5560198A (en) | 1995-05-25 | 1996-10-01 | United Technologies Corporation | Cooled gas turbine engine augmentor fingerseal assembly |
US5833139A (en) | 1995-09-06 | 1998-11-10 | United Technologies Corporation | Single variable flap exhaust nozzle |
US6301877B1 (en) | 1995-11-13 | 2001-10-16 | United Technologies Corporation | Ejector extension cooling for exhaust nozzle |
US5799874A (en) | 1995-11-30 | 1998-09-01 | United Technologies Corporation | Aerodynamically controlled ejector |
US5794851A (en) | 1995-12-07 | 1998-08-18 | United Technologies Corporation | Nozzle sealing apparatus |
US5839663A (en) | 1996-07-23 | 1998-11-24 | United Technologies Corporation | Gas turbine exhaust nozzle flap and flap seal apparatus |
US5813611A (en) | 1996-09-27 | 1998-09-29 | United Technologies Corporation | Compact pressure balanced fulcrum-link nozzle |
US5797544A (en) | 1996-09-27 | 1998-08-25 | United Technologies Corporation | C/D nozzle with synchronizing ring link suspension |
US6347510B1 (en) | 1998-12-18 | 2002-02-19 | United Technologies Corporation | Axi-nozzle ejector seal |
US6398129B1 (en) | 1999-12-29 | 2002-06-04 | United Technologies Corporation | Throat configuration for axisymmetric nozzle |
US6607355B2 (en) | 2001-10-09 | 2003-08-19 | United Technologies Corporation | Turbine airfoil with enhanced heat transfer |
US6993914B2 (en) * | 2003-08-12 | 2006-02-07 | Snecma Moteurs | Convergent-divergent turbojet nozzle |
US7032835B2 (en) * | 2004-01-28 | 2006-04-25 | United Technologies Corporation | Convergent/divergent nozzle with modulated cooling |
US20060266016A1 (en) * | 2005-05-27 | 2006-11-30 | United Technologies Corporation | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle |
US7377099B2 (en) * | 2005-05-27 | 2008-05-27 | United Technologies Corporation | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle |
US20070186555A1 (en) * | 2006-02-15 | 2007-08-16 | United Technologies Corporation | Convergent divergent nozzle with supported divergent seals |
US7624579B2 (en) * | 2006-02-15 | 2009-12-01 | United Technologies Corporation | Convergent divergent nozzle with supported divergent seals |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180156053A1 (en) * | 2011-06-30 | 2018-06-07 | United Technologies Corporation | Impingement cooled nozzle liner |
US10132181B2 (en) * | 2011-06-30 | 2018-11-20 | United Technologies Corporation | Impingement cooled nozzle liner |
US20130232949A1 (en) * | 2012-03-09 | 2013-09-12 | Gary J. Dillard | Pressure balanced area control of high aspect ratio nozzle |
US20160017815A1 (en) * | 2013-03-12 | 2016-01-21 | United Technologies Corporation | Expanding shell flow control device |
US9845768B2 (en) | 2013-03-13 | 2017-12-19 | Rolls-Royce North American Technologies, Inc. | Three stream, variable area, vectorable nozzle |
US20150292437A1 (en) * | 2013-04-12 | 2015-10-15 | United Technologies Corporation | Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface |
US9689346B2 (en) * | 2013-04-12 | 2017-06-27 | United Technologies Corporation | Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface |
US11022072B2 (en) | 2013-04-12 | 2021-06-01 | Raytheon Technologies Corporation | Gas turbine engine convergent/divergent exhaust nozzle divergent seal with preloaded dovetail interface background |
Also Published As
Publication number | Publication date |
---|---|
US20090072490A1 (en) | 2009-03-19 |
EP1956225A2 (en) | 2008-08-13 |
EP1956225A3 (en) | 2011-10-26 |
EP1956225B1 (en) | 2014-03-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8205454B2 (en) | Convergent divergent nozzle with edge cooled divergent seals | |
US7624567B2 (en) | Convergent divergent nozzle with interlocking divergent flaps | |
US7624579B2 (en) | Convergent divergent nozzle with supported divergent seals | |
US7032835B2 (en) | Convergent/divergent nozzle with modulated cooling | |
US7757477B2 (en) | Convergent divergent nozzle with slot cooled nozzle liner | |
US8961114B2 (en) | Integrated variable geometry flow restrictor and heat exchanger | |
US6286317B1 (en) | Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity | |
EP1726811B1 (en) | System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle | |
US3793827A (en) | Stiffener for combustor liner | |
US7269957B2 (en) | Combustion liner having improved cooling and sealing | |
EP1378651B1 (en) | Cooled variable geometry exhaust nozzle | |
MXPA05004420A (en) | Effusion cooled transition duct with shaped cooling holes. | |
US4171093A (en) | Durability flap and seal liner assembly for exhaust nozzles | |
EP2236750B1 (en) | An impingement cooling arrangement for a gas turbine engine | |
JPS6335897B2 (en) | ||
EP3747775B1 (en) | Nacelle with a translatable inlet for an aircraft propulsion system | |
US5842643A (en) | Articulated exhaust nozzle fairing | |
US4892254A (en) | Aircraft engine interface fairing support | |
GB2024403A (en) | Flame-holder | |
US20150122905A1 (en) | Passive tangential ejector for an exhaust nozzle of a gas turbine engine | |
GB2136508A (en) | Coolable stator assembly for a gas turbine engine | |
EP0778407B1 (en) | Nozzle sealing apparatus | |
JPH03100359A (en) | Exhaust nozzle hinge | |
EP0091786B1 (en) | Variable geometry nozzles for turbomachines | |
US20150292437A1 (en) | Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:COWAN, CURTIS C.;ALLORE, JAMES P.;ATTRIDGE, PAUL;REEL/FRAME:018857/0274 Effective date: 20070116 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 8 |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS Free format text: CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001 Effective date: 20200403 |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:055659/0001 Effective date: 20200403 |
|
AS | Assignment |
Owner name: RTX CORPORATION, CONNECTICUT Free format text: CHANGE OF NAME;ASSIGNOR:RAYTHEON TECHNOLOGIES CORPORATION;REEL/FRAME:064714/0001 Effective date: 20230714 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 12 |